Abstract: A tunable mass damper assembly is attachable to a rotor blade. The tunable mass damper assembly comprises a base configured to be attached to the rotor blade and a pendulum mass structure movably attached to the base and configured to move relative to the base in accordance with a rotational speed of the rotor blade about a rotor axis. The pendulum mass structure is configured to reduce vibratory forces of the rotor blade induced by a rotation of the rotor blade about the rotor axis. An entirety of the pendulum mass structure being configured to be contained within and enclosed by the rotor blade.

Abstract: A blade tracking system for a rotary wing aircraft includes a blade sensor mounted on a blade of the rotary wing aircraft, the blade sensor wirelessly transmitting blade data; a reference sensor mounted to the rotary wing aircraft, the blade driven by the rotor hub, the reference sensor transmitting reference data; and a processor receiving the blade data and the reference data, the processor determining at least one of lead-lag, flap and pitch of the blade in response to the blade data and the reference data.

Abstract: A method for reducing vibrations in an airframe of an aircraft includes determining, with a processor, information indicative of an initial error value between a desired vibration level and a measured vibration level in the airframe; determining, with the processor, an initial adjustment solution for the aircraft in response to the determining of the information for the initial error value; receiving, with the processor, information indicative of a flight response to the initial adjustment solution; combining, with the processor, disturbance signals indicative of vibration noise with the information for the flight response; determining, with the processor, a subsequent error value between the desired vibration level and a subsequent measured vibration level; and determining, with the processor, a predicted adjustment solution in response to the determining of the subsequent error value.

Abstract: A method for reducing vibrations in an airframe of an aircraft includes determining, with a processor, information indicative of an initial error value between a desired vibration level and a measured vibration level in the airframe; determining, with the processor, an initial adjustment solution for the aircraft in response to the determining of the information for the initial error value; receiving, with the processor, information indicative of a flight response to the initial adjustment solution; combining, with the processor, disturbance signals indicative of vibration noise with the information for the flight response; determining, with the processor, a subsequent error value between the desired vibration level and a subsequent measured vibration level; and determining, with the processor, a predicted adjustment solution in response to the determining of the subsequent error value.

Abstract: A blade tracking system for a rotary wing aircraft includes a blade sensor mounted on a blade of the rotary wing aircraft, the blade sensor wirelessly transmitting blade data; a reference sensor mounted to the rotary wing aircraft, the blade driven by the rotor hub, the reference sensor transmitting reference data; and a processor receiving the blade data and the reference data, the processor determining at least one of lead-lag, flap and pitch of the blade in response to the blade data and the reference data.

Abstract: A retractable and extensible trailer comprising: a base assembly; a moveable top assembly moveably attached to the base assembly and configured to be infinitely adjustable between a lowered position and an upper position; a trailer substructure in communication with the base assembly; a base front and/or rear folding door located at the front and/or rear of the base assembly and in rotative communication with the trailer substructure. The base front and/or rear folding door comprises: an upper ramp in rotative communication with the trailer substructure; at least one locking plate in fixed communication with the upper ramp; at least one connector plate in rotative communication with the at least one locking plate; and a lower ramp in fixed communication with the at least one connector plate.